Modal analysis of laminated composite beams reinforced with randomly oriented fibers for aeronautical engine applications

Turbine blades are integral components of aircraft engines, directly influencing performance, efficiency, and safety. These blades operate under extreme conditions, facing high temperatures, significant mechanical stresses, and corrosive environments. Therefore, the selection of appropriate materials for turbine blades is crucial to ensure their reliability, engine efficiency and longevity. The present paper is focused on modal analysis of the laminate beam in layers’ carbon (mast) / ceramic. In this study, we use the Euler-Bernoulli hypothesis for the fins which considered the fin as a simple beam. The simulation was performed using Ansys software to assess the natural frequencies and mode shapes of the laminated beam under bending loads. The results compared to those of beams made from supper alloys used in aircraft engines. The findings reveal that the laminate composite beam exhibits greater dynamic stability than its alloy counterparts. This enhanced stability suggests that laminated composite materials are particularly suited for high-pressure applications, where performance and reliability are critical. Notably, the composite material with carbon mast (HM) demonstrates superior mechanical properties, including increased rigidity, reduced micro-cracking, improve efficiency and performance of flight engines and increased lifetime. Finally, this study underscores the importance of innovative materials in aeronautical engineering, highlighting the advantages of laminated composites in dynamic applications.